# Geostationary orbit

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A geostationary orbit, also referred to as a geosynchronous equatorial orbit [lower-alpha 1] (GEO), is a circular geosynchronous orbit 35,786 kilometres (22,236 miles) above Earth's equator and following the direction of Earth's rotation.

A circular orbit is the orbit with a fixed distance around the barycenter, that is, in the shape of a circle.

A geosynchronous orbit is an orbit around Earth of a satellite with an orbital period that matches Earth's rotation on its axis, which takes one sidereal day. The synchronization of rotation and orbital period means that, for an observer on Earth's surface, an object in geosynchronous orbit returns to exactly the same position in the sky after a period of one sidereal day. Over the course of a day, the object's position in the sky may remain still or trace out a path, typically in a figure-8 form, whose precise characteristics depend on the orbit's inclination and eccentricity. Satellites are typically launched in an eastward direction. A circular geosynchronous orbit is 35,786 km (22,236 mi) above Earth's surface. Those closer to Earth orbit faster than Earth rotates, so from Earth, they appear to move eastward while those that orbit beyond geosynchronous distances appear to move westward.

The equator of a rotating spheroid is the parallel at which latitude is defined to be 0°. It is the imaginary line on the spheroid, equidistant from its poles, dividing it into northern and southern hemispheres. In other words, it is the intersection of the spheroid with the plane perpendicular to its axis of rotation and midway between its geographical poles.

## Contents

An object in such an orbit has an orbital period equal to the Earth's rotational period, one sidereal day, and so to ground observers it appears motionless, in a fixed position in the sky. The concept of a geostationary orbit was popularised by Arthur C. Clarke in the 1940s as a way to revolutionise telecommunications, and the first satellite to be placed in this kind of orbit was launched in 1963.

The orbital period is the time a given astronomical object takes to complete one orbit around another object, and applies in astronomy usually to planets or asteroids orbiting the Sun, moons orbiting planets, exoplanets orbiting other stars, or binary stars.

Sir Arthur Charles Clarke was a British science fiction writer, science writer and futurist, inventor, undersea explorer, and television series host.

In the context of spaceflight, a satellite is an object that has been intentionally placed into orbit. These objects are called artificial satellites to distinguish them from natural satellites such as Earth's Moon.

Communications satellites are often placed in a geostationary orbit so that Earth-based satellite antennas (located on Earth) do not have to rotate to track them, but can be pointed permanently at the position in the sky where the satellites are located. Weather satellites are also placed in this orbit for real time monitoring and data collection, and navigation satellites to provide a known calibration point and enhance GPS accuracy.

A communications satellite is an artificial satellite that relays and amplifies radio telecommunications signals via a transponder; it creates a communication channel between a source transmitter and a receiver at different locations on Earth. Communications satellites are used for television, telephone, radio, internet, and military applications. There are 2,134 communications satellites in Earth's orbit, used by both private and government organizations. Many are in geostationary orbit 22,236 miles (35,785 km) above the equator, so that the satellite appears stationary at the same point in the sky, so the satellite dish antennas of ground stations can be aimed permanently at that spot and do not have to move to track it.

A satellite dish is a dish-shaped type of parabolic antenna designed to receive or transmit information by radio waves to or from a communication satellite. The term most commonly means a dish used by consumers to receive direct-broadcast satellite television from a direct broadcast satellite in geostationary orbit.

The weather satellite is a type of satellite that is primarily used to monitor the weather and climate of the Earth. Satellites can be polar orbiting, covering the entire Earth asynchronously, or geostationary, hovering over the same spot on the equator.

Geostationary satellites are launched via a temporary orbit, and placed in a slot above a particular point on the Earth's surface. The orbit requires some stationkeeping to keep its position, and modern retired satellites are placed in a higher graveyard orbit to avoid collisions.

A parking orbit is a temporary orbit used during the launch of a satellite or other space probe. A launch vehicle boosts into the parking orbit, then coasts for a while, then fires again to enter the final desired trajectory. The alternative to a parking orbit is direct injection, where the rocket fires continuously until its fuel is exhausted, ending with the payload on the final trajectory.

A graveyard orbit, also called a junk orbit or disposal orbit, is an orbit that lies away from common operational orbits. One significant graveyard orbit is a supersynchronous orbit well above geosynchronous orbit. Satellites are typically moved into such orbits at the end of their operational life to reduce the probability of colliding with operational spacecraft and generating space debris.

## History

The first appearance of a geostationary orbit in popular literature was in October 1942, in the first Venus Equilateral story by George O. Smith, [1] but Smith did not go into details. British science fiction author Arthur C. Clarke popularised and expanded the concept in a 1945 paper entitled Extra-Terrestrial Relays – Can Rocket Stations Give Worldwide Radio Coverage?, published in Wireless World magazine. Clarke acknowledged the connection in his introduction to The Complete Venus Equilateral. [2] [3] The orbit, which Clarke first described as useful for broadcast and relay communications satellites, [3] is sometimes called the Clarke Orbit. [4] Similarly, the collection of artificial satellites in this orbit is known as the Clarke Belt. [5]

The Venus Equilateral series is a set of 13 science fiction short stories by American writer George O. Smith, concerning the Venus Equilateral Relay Station, an interplanetary communications hub located at the L4 Lagrangian point of the Sun-Venus system. Most of the stories were first published in Astounding Science Fiction between 1942 and 1945.

George Oliver Smith was an American science fiction author. He is not to be confused with George H. Smith, another American science fiction author.

Science fiction is a genre of speculative fiction that has been called the "literature of ideas". It typically deals with imaginative and futuristic concepts such as advanced science and technology, time travel, parallel universes, fictional worlds, space exploration, and extraterrestrial life. It often explores the potential consequences of scientific innovations.

In technical terminology the orbit is referred to as either a geostationary or geosynchronous equatorial orbit, with the terms used somewhat interchangeably. [6]

The first geostationary satellite was designed by Harold Rosen while he was working at Hughes Aircraft in 1959. Inspired by Sputnik 1, he wanted to use a geostationary satellite to globalise communications. Telecommunications between the US and Europe was then possible between just 136 people at a time, and reliant on high frequency radios and an undersea cable. [7]

Conventional wisdom at the time was that it would require too much rocket power to place a satellite in a geostationary orbit and it would not survive long enough to justify the expense, [8] so early efforts were put towards constellations of satellites in low or medium Earth orbit. [9] The first of these were the passive Echo balloon satellites in 1960, followed by Telstar 1 in 1962. [10] Although these projects had difficulties with signal strength and tracking, that could be solved through geostationary satellites, the concept was seen as impractical, so Hughes often withheld funds and support. [9] [7]

By 1961, Rosen and his team had produced a cylindrical prototype with a diameter of 76 centimetres (30 in), height of 38 centimetres (15 in), weighing 11.3 kilograms (25 lb), light and small enough to be placed into orbit. It was spin stabilised with a dipole antenna producing a pancake shaped waveform. [11] In August 1961, they were contracted to began building the real satellite. [7] They lost Syncom 1 to electronics failure, but Syncom 2 was successfully placed into a geosynchronous orbit in 1963. Although its inclined orbit still required moving antennas, it was able to relay TV transmissions, and allowed for US President John F. Kennedy to phone Nigerian prime minister Abubakar Tafawa Balewa from a ship on August 23, 1963. [9] [12]

The first satellite placed in a geostationary orbit was Syncom 3, which was launched by a Delta D rocket in 1963. [13] With its increased bandwidth, this satellite was able to transmit live coverage of the Summer Olympics from Japan to America. Geostationary orbits have been in common use ever since, in particular for satellite television. [9]

Today there are hundreds of geostationary satellites providing remote sensing and communications. [7] [14]

Although most populated land locations on the planet now have terrestrial communications facilities (microwave, fiber-optic), with telephone access covering 96% of the population and internet access 90%, [15] some rural and remote areas in developed countries are still reliant on satellite communications. [16] [17]

## Uses

Most commercial communications satellites, broadcast satellites and SBAS satellites operate in geostationary orbits. [18] [19] [20]

### Communications

Geostationary communication satellites are useful because they are visible from a large area of the earth's surface, extending 81° away in both latitude and longitude. [21] They appear stationary in the sky, which eliminates the need for ground stations to have movable antennas. This means that Earth based observers can erect small, cheap and stationary antennas that are always directed at the desired satellite. [22] :537 However, latency becomes significant as it takes about 240ms for a signal to pass from a ground based transmitter on the equator to the satellite and back again. [22] :538 This delay presents problems for latency-sensitive applications such as voice communication, [23] so geostationary communication satellites are primarily used for unidirectional entertainment and applications where low latency alternatives are not available. [24]

Geostationary satellites are directly overhead at the equator and appear lower in the sky to an observer nearer the poles. As the observer's latitude increases, communication becomes more difficult due to factors such as atmospheric refraction, Earth's thermal emission, line-of-sight obstructions, and signal reflections from the ground or nearby structures. At latitudes above about 81°, geostationary satellites are below the horizon and cannot be seen at all. [21] Because of this, some Russian communication satellites have used elliptical Molniya and Tundra orbits, which have excellent visibility at high latitudes. [25]

### Meteorology

A worldwide network of operational geostationary meteorological satellites is used to provide visible and infrared images of Earth's surface and atmosphere for weather observation, oceanography, and atmospheric tracking. As of 2019 there are 19 satellites in either operation or stand-by. [26] These satellite systems include:

These satellites typically captures images in the visual and infrared spectrum with a spatial resolution between 0.5 and 4 square kilometres. [34] The coverage is typically 70°, [34] and in some cases less. [35]

Geostationary satellite imagery has been used for tracking volcanic ash, [36] measuring cloud top temperatures and water vapour, oceanography, [37] measuing land temperature and vegetation coverage, [38] facilitating cyclone path prediction, [33] and providing real time cloud coverage and other tracking data. [39] Some information has been incorporated into meteorological prediction models, but due to their wide field of view, full-time monitoring and lower resolution, geostationary weather satellite images are primarily used for short-term and real-time forecasting. [40] [38]

Geostationary satellites can be used to augment GNSS systems by relaying clock, ephemeris and ionospheric error corrections (calculated from ground stations of a known position) and providing an additional reference signal. [41] [42] This improves position accuracy from approximately 5m to 1m or less. [43]

Past and current navigation systems that use geostationary satellites include:

## Implementation

### Launch

An example of a transition from GTO to GSO.
·.

Geostationary satellites are launched to the east into a prograde orbit that matches the rotation rate of the equator. The smallest inclination that a satellite can be launched into is that of the launch site's latitude, so launching the satellite from the close to the equator limits the amount of inclination change needed later. [47] Additionlly, launching from close to the equator allows the speed of the Earth's rotation to give the satellite a boost. A launch site should have water or deserts to the east, so any failed rockets won't fall on a populated area. [48]

Most launch vehicles place geostationary satellites directly into a geostationary transfer orbit (GTO), an elliptical orbit with an apogee at GEO height and a low perigee. On-board satellite propulsion is then used to raise the perigee, circularise and reach GEO. [47] [49]

### Orbit allocation

Satellites in geostationary orbit must all occupy a single ring above the equator. The requirement to space these satellites apart, to avoid harmful radio-frequency interference during operations, means that there are a limited number of orbital slots available, and thus only a limited number of satellites can be operated in geostationary orbit. This has led to conflict between different countries wishing access to the same orbital slots (countries near the same longitude but differing latitudes) and radio frequencies. These disputes are addressed through the International Telecommunication Union's allocation mechanism. [50] [51] In the 1976 Bogotá Declaration, eight countries located on the Earth's equator claimed sovereignty over the geostationary orbits above their territory, but the claims gained no international recognition. [52]

### Statite proposal

A statite is a hypothetical satellite that uses radiation pressure from the sun against a solar sail to modify its orbit.

It would hold its location over the dark side of the Earth at a latitude of approximately 30 degrees. A statite is stationary relative to the Earth and Sun system rather than compared to surface of the Earth, and could ease congestion in the geostationary ring. [53] [54]

## Retired satellites

Geostationary satellites require some station keeping to keep their position, and once they run out of thruster fuel they are generally retired. The transponders and other onboard systems often outlive the thruster fuel and by allowing the satellite to move naturally into an inclined geosynchronous orbit some satellites can remain in use, [55] [56] or else be elevated to a graveyard orbit. This process is becoming increasingly regulated and satellites must have a 90% chance of moving over 200 km above the geostationary belt at end of life. [57]

### Space debris

Space debris at geostationary orbits typically has a lower collision speed than at LEO since all GEO satellites orbit in the same plane, altitude and speed, however the presence of satellites in eccentric orbits allows for collisions at up to 4 km/s. Although a collision is comparatively unlikely, GEO satellites have a limited ability to avoid any debris. [58]

Debris less than 10 cm in diameter can't be seen from the Earth, making it difficult to assess their prevalence. [59]

Despite efforts to reduce risk, spacecraft collisions have occurred. The European Space Agency telecom satellite Olympus-1 was struck by a meteoroid on August 11, 1993 and eventually moved to a graveyard orbit, [60] and in 2006 the Russian Express-AM11 communications satellite was struck by an unknown object and rendered inoperable, [61] although its engineers had enough contact time with the satellite to send it into a graveyard orbit. In 2017 both AMC-9 and Telkom-1 broke apart from an unknown cause. [62] [59] [63]

## Properties

A typical geostationary orbit has the following properties:

### Inclination

An inclination of zero ensures that the orbit remains over the equator at all times, making it stationary with respect to latitude from the point of view of a ground observer (and in the ECEF reference frame). [22] :122

### Period

The orbital period is equal to exactly one sidereal day. This means that the satellite will return to the same point above the Earth's surface every (sidereal) day, regardless of other orbital properties. For a geostationary orbit in particular, it ensures that it holds the same longitude over time. [22] :121 This orbital period, T, is directly related to the semi-major axis of the orbit through the formula:

${\displaystyle T=2\pi {\sqrt {a^{3} \over \mu }}}$

where:

a is the length of the orbit's semi-major axis
${\displaystyle \mu }$ is the standard gravitational parameter of the central body [22] :137

### Eccentricity

The eccentricity is zero, which produces a circular orbit. This ensures that the satellite doesn't move closer or further away from the Earth, which would cause it to track backwards and forwards across the sky. [22] :122

### Orbital stability

A geostationary orbit can be achieved only at an altitude very close to 35,786 kilometres (22,236 miles) and directly above the equator. This equates to an orbital speed of 3.07 kilometres per second (1.91 miles per second) and an orbital period of 1,436 minutes, one sidereal day. This ensures that the satellite will match the Earth's rotational period and has a stationary footprint on the ground. All geostationary satellites have to be located on this ring.

A combination of lunar gravity, solar gravity, and the flattening of the Earth at its poles causes a precession motion of the orbital plane of any geostationary object, with an orbital period of about 53 years and an initial inclination gradient of about 0.85° per year, achieving a maximal inclination of 15° after 26.5 years. [64] [22] :156 To correct for this perturbation, regular orbital stationkeeping maneuvers are necessary, amounting to a delta-v of approximately 50 m/s per year. [65]

A second effect to be taken into account is the longitudinal drift, caused by the asymmetry of the Earth – the equator is slightly elliptical. [22] :156 There are two stable equlilibrium points (at 75.3°E and 252°E) and two corresponding unstable points (at 165.3°E and 14.7°W). Any geostationary object placed between the equilibrium points would (without any action) be slowly accelerated towards the stable equilibrium position, causing a periodic longitude variation. [64] The correction of this effect requires station-keeping maneuvers with a maximal delta-v of about 2 m/s per year, depending on the desired longitude. [65]

Solar wind and radiation pressure also exert small forces on satellites: over time, these cause them to slowly drift away from their prescribed orbits. [66]

In the absence of servicing missions from the Earth or a renewable propulsion method, the consumption of thruster propellant for station-keeping places a limitation on the lifetime of the satellite. Hall-effect thrusters, which are currently in use, have the potential to prolong the service life of a satellite by providing high-efficiency electric propulsion. [65]

### Derivation of geostationary altitude

For circular orbits around a body, the centripetal force required to maintain the orbit (Fc) is equal to the gravitational force acting on the satellite (Fg): [67]

${\displaystyle F_{c}=F_{g}}$
${\displaystyle F_{g}=G{\frac {M_{E}m_{s}}{r^{2}}}}$,

where Fg is the gravitational force acting between two objects, ME is the mass of the Earth, 5.9736 × 1024 kg, ms is the mass of the satellite, r is the distance between the centers of their masses, and G is the gravitational constant, (6.67428 ± 0.00067) × 10−11 m3 kg−1 s−2. [67]

The magnitude of the acceleration (a) of a body moving in a circle is given by:

${\displaystyle a={\frac {v^{2}}{r}}}$

where v is the magnitude of the velocity (i.e. the speed) of the satellite. From Newton's Second law of Motion, the centripetal force Fc is given by:

${\displaystyle F_{c}=m_{s}{\frac {v^{2}}{r}}}$. [67]

As Fc = Fg,

${\displaystyle {\frac {v^{2}}{r}}=G{\frac {M_{E}m_{s}}{r^{2}}}}$,

so that

${\displaystyle {v^{2}}=G{\frac {M_{E}}{r}}}$

Replacing v with the equation for the speed of an object moving around a circle produces:

${\displaystyle \left({\frac {2\pi r}{T}}\right)^{2}=G{\frac {M_{E}}{r}}}$

where T is the orbital period (i.e. one sidereal day), and is equal to 86164.09054 s. [68] This gives an equation for r: [69]

${\displaystyle r={\sqrt[{3}]{\frac {G{M_{E}}T^{2}}{4\pi ^{2}}}}}$

The product GME is known with much greater precision than either factor alone; it is known as the geocentric gravitational constant μ = 398,600.4418 ± 0.0008 km3 s−2. Hence

${\displaystyle \mathbf {r} ={\sqrt[{3}]{\frac {{\boldsymbol {\mu }}\mathbf {T} ^{2}}{\mathbf {4} {\boldsymbol {\pi }}^{2}}}}}$

The resulting orbital radius is 42,164 kilometres (26,199 miles). Subtracting the Earth's equatorial radius, 6,378 kilometres (3,963 miles), gives the altitude of 35,786 kilometres (22,236 miles). [70]

The orbital speed is calculated by multiplying the angular speed by the orbital radius:

${\displaystyle v=\omega r\quad \approx 3074.6~{\text{m/s}}}$

### Mars

By the same method, we can determine the orbital altitude for any similar pair of bodies, including the areostationary orbit of an object in relation to Mars, if it is assumed that it is spherical (which it is not). [71] The gravitational constant GM (μ) for Mars has the value of 42,830 km3s−2, its equatorial radius is 3389.50 km and the known rotational period (T) of the planet is 1.02595676 Earth days (88,642.66 seconds). Using these values, Mars' orbital altitude is equal to 17,035 km. [72]

## Notes

1. Geostationary orbit and Geosynchronous (equatorial) orbit are used interchangeably in sources.
2. Orbital periods and speeds are calculated using the relations 4π2R3 = T2GM and V2R = GM, where R = radius of orbit in metres, T = orbital period in seconds, V = orbital speed in m/s, G = gravitational constant ≈ 6.673×1011 Nm2/kg2, M = mass of Earth ≈ 5.98×1024 kg.
3. The Moon's orbit is not perfectly circular, and is approximately 8.6 times further away from the Earth than the geostationary ring when the moon is at perigee (363104 km ÷ 42164 km) and 9.6 times further away when the moon is at apogee (405,696 km ÷ 42,164 km).

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This article incorporates  public domain material from the General Services Administration document "Federal Standard 1037C" (in support of MIL-STD-188 ).